Fan drive gear system including a two-piece fan shaft with lubricant transfer leakage recapture

ABSTRACT

A disclosed fan drive gear system for a gas turbine engine includes a first fan shaft coupled to a second fan shaft, a first shaft support bearing assembly disposed about the first fan shaft and a second shaft support bearing assembly disposed about the second fan shaft. A planetary gear system is coupled to the second fan shaft. A transfer bearing is configured to receive lubricant from a lubricant input and is positioned between the first and second fan shaft support bearings. A second bearing is configured to rotate with the second fan shaft and receive lubricant from the transfer bearing and communicate lubricant to at least one lubricant passage and a conduit fluidly connecting the at least one lubricant passage to the planetary gear system.

CROSS REFERENCE TO RELATED APPLICATION

This application claims priority to U.S. Provisional Application No.61/921,791 filed on Dec. 30, 2013.

BACKGROUND

A gas turbine engine typically includes a fan section, a compressorsection, a combustor section and a turbine section. Air entering thecompressor section is typically compressed and delivered into thecombustion section where it is mixed with fuel and ignited to generate ahigh-speed exhaust gas flow. The high-speed exhaust gas flow typicallyexpands through the turbine section to drive the compressor and the fansection.

A speed reduction device such as an epicyclical gear assembly may beutilized to drive the fan section such that the fan section may rotateat a speed different than the turbine section so as to increase theoverall propulsive efficiency of the engine. In such enginearchitectures, a shaft driven by one of the turbine sections provides aninput to the epicyclical gear assembly that drives the fan section at areduced speed such that both the turbine section and the fan section canrotate at closer to optimal speeds.

The fan section includes a plurality of fan blades mounted to a hubsupported by bearings for rotation about the engine axis. The hub iscoupled to an output of the geared architecture. The bearings requirelubricant that is supplied through lubricant passages. The gearedarchitecture also requires lubricant. The structures required forcommunicating lubricant to the bearings and geared architecture cancomplicate assembly and require additional space.

Although geared architectures have improved propulsive efficiency,turbine engine manufacturers continue to seek further improvements toengine performance including improvements to thermal, transfer andpropulsive efficiencies.

SUMMARY

A lubrication system according to an exemplary embodiment of thisdisclosure, among other possible things includes a transfer bearingconfigured to receive a lubricant from a lubricant input, a secondbearing configured to rotate with a fan drive shaft, the transferbearing engages the second bearing disposed between two fan shaftsupport bearings and is configured to transfer lubricant from thetransfer bearing to the second bearing and into at least one lubricantpassage, and a conduit fluidly connected to the at least one lubricantpassage and configured to deliver lubricant to at least one component ofa fan drive gear system.

In a further embodiment of any of the foregoing lubrication systems,includes a first race on the transfer bearing configured to transferlubricant to a first opening in registration with the at least onelubricant passage.

In a further embodiment of any of the foregoing lubrication systems, thesecond bearing includes a portion of a fan drive shaft and the at leastone lubricant passage is defined within the fan drive shaft.

In a further embodiment of any of the foregoing lubrication systems, thesecond bearing includes a portion of the fan drive shaft and a lubricantmanifold is attached for rotation with the fan drive shaft and includesthe at least one lubricant passage.

In a further embodiment of any of the foregoing lubrication systems,includes a feed tube supplying lubricant to the transfer bearing. Thefeed tube extends through an opening in a spacer defining a desiredspacing between two fan drive shaft support bearings.

In a further embodiment of any of the foregoing lubrication systems,includes at least one fastener securing at least one of the two fandrive shaft support bearings in position. The at least one fastenerincludes a scoop for catching and directing lubricant to one of the twofan drive shaft support bearings.

In a further embodiment of any of the foregoing lubrication systems, thetwo fan drive shaft support bearings include tapered bearings.

In a further embodiment of any of the foregoing lubrication systems, thetwo fan drive shaft support bearings include roller bearings.

In a further embodiment of any of the foregoing lubrication systems, thetwo fan drive shaft support bearings include ball bearings.

In a further embodiment of any of the foregoing lubrication systems, thetransfer bearing and the second bearing are disposed about a rotationalaxis.

In a further embodiment of any of the foregoing lubrication systems, theconduit is parallel to the rotational axis.

A fan drive gear system for a gas turbine engine according to anexemplary embodiment of this disclosure, among other possible thingsincludes a first fan shaft coupled to a second fan shaft. A first shaftsupport bearing assembly is disposed about the first fan shaft and asecond shaft support bearing assembly disposed about the second fanshaft. A planetary gear system is coupled to the second fan shaft. Atransfer bearing is configured to receive lubricant from a lubricantinput engaged to the fan shaft between the first shaft support bearingassembly and the second shaft support bearing assembly. A second bearingis configured to rotate with the second fan shaft and receive lubricantfrom the transfer bearing and communicate lubricant to at least onelubricant passage. A conduit fluidly connects the at least one lubricantpassage to the planetary gear system.

In a further embodiment of any of the foregoing systems, includes afirst race on the transfer bearing configured to transfer lubricant tothe at least one lubricant passage.

In a further embodiment of any of the foregoing systems, includes acarrier supporting rotation of a plurality of planet gears and thesecond shaft includes a torque shaft attached to the carrier.

In a further embodiment of any of the foregoing systems, the at leastone lubricant passage is defined within the torque shaft.

In a further embodiment of any of the foregoing systems, includes alubricant manifold attached to the second shaft and defining the atleast one lubricant passage.

In a further embodiment of any of the foregoing systems, includes aspacer between the first shaft support bearing assembly and the secondshaft support bearing assembly.

In a further embodiment of any of the foregoing systems, includes a feedtube extending through the spacer to the transfer bearing.

In a further embodiment of any of the foregoing systems, includes afirst nut holding the first shaft support bearing in place and a secondnut holding the second shaft support bearing in place. Each of the firstnut and the second nut includes a scoop for catching and directinglubricant to a corresponding one of the first and second shaft supportbearings.

A method of assembling a fan drive gear system according to an exemplaryembodiment of this disclosure, among other possible things includesattaching a torque shaft to a component of a fan drive gear system,assembling a first shaft support bearing to the torque shaft andsecuring the first shaft support bearing with a first fastener,assembling a transfer bearing to the torque shaft for communicatinglubricant to at least one lubricant passage, coupling a hub shaft to thetorque shaft, and assembling a second shaft support bearing to the hubshaft and securing the second shaft support bearing with a secondfastener spaced apart from the first shaft support bearing.

In a further embodiment of any of the foregoing methods, includesassembling a conduit for transferring lubricant from the at least onelubricant passage to the component of the fan drive gear system.

In a further embodiment of any of the foregoing methods, includesattaching a lubricant manifold to the torque shaft including the atleast one lubricant passage.

In a further embodiment of any of the foregoing methods, the componentof the fan drive gear system includes a carrier supporting rotation of aplurality of planetary gears driven by a sun gear and circumscribed by aring gear.

In a further embodiment of any of the foregoing methods, each of thefirst fastener and the second fastener includes a scoop and the assemblyof each of the fasteners comprises aligning the scoop relative to thetransfer bearing for enabling capture and transfer of lubricant to acorresponding one of the first shaft support bearing and the secondshaft support bearing.

Although the different examples have the specific components shown inthe illustrations, embodiments of this disclosure are not limited tothose particular combinations. It is possible to use some of thecomponents or features from one of the examples in combination withfeatures or components from another one of the examples.

These and other features disclosed herein can be best understood fromthe following specification and drawings, the following of which is abrief description.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic view of an example gas turbine engine.

FIG. 2 is a schematic view of a lubrication system for a fan drive gearsystem of a gas turbine engine.

FIG. 3A is a cross-sectional view of a lubricant transfer bearingassembly.

FIG. 3B is a cross-sectional view of a pinned connection of the examplelubricant transfer bearing assembly.

FIG. 3C is a cross-sectional view of a link connection of the examplelubricant transfer bearing assembly.

FIG. 3D is a cross-sectional view of the example lubricant transferbearing assembly.

FIG. 4 is a cross-sectional view of an example lubricant conduit.

FIG. 5 is a schematic view of another lubrication system for a fan drivegear assembly.

DETAILED DESCRIPTION

FIG. 1 schematically illustrates a gas turbine engine 20. The gasturbine engine 20 is disclosed herein as a two-spool turbofan thatgenerally incorporates a fan section 22, a compressor section 24, acombustor section 26 and a turbine section 28. Alternative engines mightinclude an augmentor section (not shown) among other systems orfeatures. The fan section 22 drives air along a bypass flow path B in abypass duct defined within a nacelle 15 while the compressor section 24drives air along a core flow path C for compression and communicationinto the combustor section 26 then expansion through the turbine section28. Although depicted as a two-spool turbofan gas turbine engine in thedisclosed non-limiting embodiment, it should be understood that theconcepts described herein are not limited to use with two-spoolturbofans as the teachings may be applied to other types of turbineengines including three-spool architectures.

The exemplary engine 20 generally includes a low speed spool 30 and ahigh speed spool 32 mounted for rotation about an engine centrallongitudinal axis A relative to an engine static structure 36 viaseveral bearing systems 38. It should be understood that various bearingsystems 38 at various locations may alternatively or additionally beprovided and the location of bearing systems 38 may be varied asappropriate to the application.

The low speed spool 30 generally includes an inner shaft 40 thatinterconnects a fan 42, a first (or low) pressure compressor 44 and afirst (or low) pressure turbine 46. The inner shaft 40 is connected tothe fan 42 through a speed change mechanism, which in exemplary gasturbine engine 20 is illustrated as a geared architecture 48 to drivethe fan 42 at a lower speed than the low speed spool 30. The high speedspool 32 includes an outer shaft 50 that interconnects a second (orhigh) pressure compressor 52 and a second (or high) pressure turbine 54.A combustor 56 is arranged in exemplary gas turbine 20 between the highpressure compressor 52 and the high pressure turbine 54. A mid-turbineframe 58 of the engine static structure 36 is arranged generally betweenthe high pressure turbine 54 and the low pressure turbine 46. Themid-turbine frame 58 further supports bearing systems 38 in the turbinesection 28. The inner shaft 40 and the outer shaft 50 are concentric androtate via bearing systems 38 about the engine central longitudinal axisA which is collinear with their longitudinal axes.

Airflow through the core flow path C is compressed by the low pressurecompressor 44 then the high pressure compressor 52, mixed and burnedwith fuel in the combustor 56, then expanded over the high pressureturbine 54 and low pressure turbine 46. The mid-turbine frame 58includes airfoils 60 which are in the core flow path C. The turbines 46,54 rotationally drive the respective low speed spool 30 and high speedspool 32 in response to the expansion. It will be appreciated that eachof the positions of the fan section 22, compressor section 24, combustorsection 26, turbine section 28, and fan drive gear system 48 may bevaried. For example, gear system 48 may be located aft of combustorsection 26 or even aft of turbine section 28, and fan section 22 may bepositioned forward or aft of the location of gear system 48.

The engine 20 in one example is a high-bypass geared aircraft engine. Ina further example, the engine 20 bypass ratio is greater than about six(6), with an example embodiment being greater than about ten (10), thegeared architecture 48 is an epicyclic gear train, such as a planetarygear system or other gear system, with a gear reduction ratio of greaterthan about 2.3 and the low pressure turbine 46 has a pressure ratio thatis greater than about five. In one disclosed embodiment, the engine 20bypass ratio is greater than about ten (10:1), the fan diameter issignificantly larger than that of the low pressure compressor 44, andthe low pressure turbine 46 has a pressure ratio that is greater thanabout five 5:1. Low pressure turbine 46 pressure ratio is pressuremeasured prior to inlet of low pressure turbine 46 as related to thepressure at the outlet of the low pressure turbine 46 prior to anexhaust nozzle. The geared architecture 48 may be an epicycle geartrain, such as a planetary gear system or other gear system, with a gearreduction ratio of greater than about 2.3:1. It should be understood,however, that the above parameters are only exemplary of one embodimentof a geared architecture engine and that the present invention isapplicable to other gas turbine engines including direct driveturbofans.

A significant amount of thrust is provided by the bypass flow B due tothe high bypass ratio. The fan section 22 of the engine 20 is designedfor a particular flight condition—typically cruise at about 0.8 Mach andabout 35,000 feet. The flight condition of 0.8 Mach and 35,000 ft, withthe engine at its best fuel consumption—also known as “bucket cruiseThrust Specific Fuel Consumption (‘TSFC’)”—is the industry standardparameter of lbm of fuel being burned divided by lbf of thrust theengine produces at that minimum point. “Low fan pressure ratio” is thepressure ratio across the fan blade alone, without a Fan Exit Guide Vane(“FEGV”) system. The low fan pressure ratio as disclosed hereinaccording to one non-limiting embodiment is less than about 1.45. “Lowcorrected fan tip speed” is the actual fan tip speed in ft/sec dividedby an industry standard temperature correction of [(Tram ° R)/(518.7°R)]^(0.5). The “Low corrected fan tip speed” as disclosed hereinaccording to one non-limiting embodiment is less than about 1150ft/second.

The example gas turbine engine includes the fan 42 that comprises in onenon-limiting embodiment less than about twenty-six (26) fan blades. Inanother non-limiting embodiment, the fan section 22 includes less thanabout twenty (20) fan blades. Moreover, in one disclosed embodiment thelow pressure turbine 46 includes no more than about six (6) turbinerotors schematically indicated at 34. In another non-limiting exampleembodiment the low pressure turbine 46 includes about three (3) turbinerotors. A ratio between the number of fan blades 42 and the number oflow pressure turbine rotors is between about 3.3 and about 8.6. Theexample low pressure turbine 46 provides the driving power to rotate thefan section 22 and therefore the relationship between the number ofturbine rotors 34 in the low pressure turbine 46 and the number ofblades 42 in the fan section 22 disclose an example gas turbine engine20 with increased power transfer efficiency.

A fan drive gear system 66 of the example gas turbine engine 20 includesthe geared architecture 48 and a shaft assembly 76. A lubrication system62 supplies lubricant to the geared architecture 48 and to a bearingsystem 95 that supports rotation of the shaft assembly 76. In thisexample, a fan hub 64 is part of the shaft assembly 76. The shaftassembly 76 includes two parts and is coupled to the geared architecture48 to drive the fan hub 64 and thereby the plurality of fan blades 42about the axis A.

Referring to FIG. 2 with continued reference to FIG. 1, the fan drivegear system 66 is provided lubricant from the lubricant system 62. Theexample geared architecture 48 includes a sun gear 68 that is driven bythe inner shaft 40. The sun gear 68 in turn drives intermediate gears 70that are supported within a carrier 72. The intermediate gears 70 are inturn engaged to a ring gear 74 that circumscribes the plurality ofintermediate gears 70. Each of the intermediate gears 70 is supported ona journal bearing 124 that requires lubricant. Moreover, the gearedarchitecture 48 requires lubricant to various portions to maintaindesired power transfer efficiency.

Lubrication is supplied from the lubricant system 62 to a feeder tube106. The feed tube 106 supplies lubricant to a stationary lubricanttransfer bearing assembly 84. The transfer bearing assembly 84communicates lubricant to a second bearing 85. In this example, thesecond bearing 85 is an outer surface of a portion of the fan shaftassembly 76. The lubricant transfer bearing assembly 84 includes carbonseals 86 that engage the rotating second bearing 85 of the shaftassembly 76.

In this example, the shaft assembly 76 includes a hub shaft 78 and atorque shaft 80. The torque shaft 80 in this example is coupled to thecarrier 72 to transfer rotational output from the geared architecture48.

The example fan shaft assembly 76 is supported by a first fan driveshaft support bearing assembly 92 and a second fan drive shaft supportbearing assembly 94. The example transfer bearing assembly 84 isdisposed between the first and second fan drive shaft support bearingassembles 92 and 94. The bearing assemblies 92 and 94 support rotationof the fan shaft assembly 76.

Each of the fan drive support bearing assemblies 92, 94 includes aninner race 110 that rotates with a corresponding portion of the fanshaft assembly 76. Each of the fan shaft support bearing assemblies 92,94 includes outer races 112 supported on an engine static structure 36.The bearing assemblies 92 and 94 are spaced apart by a spring spacer 96.The spring spacer 96 defines the spacing between the first bearing 92and the second bearing 94 and provides a preload on the bearingsassemblies 92 and 94.

The spring spacer 96 includes an opening 104 through which the feed tube106 extends. The feed tube 106 includes a seal head portion 108 thatfits within the transfer bearing assembly 84. The transfer bearingassembly 84 includes openings that correspond with passages 100 throughthe torque shaft 80. The openings 100 communicate lubricant 15 suppliedfrom the lubricant supply system 62 through the feed tube 106 to anintermediate lubricant passage 88. As appreciated, in this example, asingle lubricant passage 88 is shown. However, a plurality of passages88 may be utilized to communicate lubricant to different parts of thegeared architecture 48.

In this example, a lubricant manifold 98 is attached to the torque shaft80 and rotates with the torque shaft 80 about the axis A. The examplelubricant manifold includes seals 95 that seal against an interiorsurface of the torque shaft 80. Lubricant provided through the feed tube106 passes through openings 100 within the torque shaft 80 to theintermediate lubricant passage 88. From the intermediate lubricantpassage 88, lubricant is passed through a conduit 90 to passages 102defined within the carrier assembly 72.

As appreciated, although the passages 102 are defined in this disclosedexample within the carrier 72, the passages 102 can be within otherfeatures or structures of the geared architecture 48 to communicatelubricant to specific locations. In this example, the passage 102communicates lubricant to the journal bearing 124 supporting rotation ofa corresponding intermediate gear 70.

Each of the shaft support bearing assemblies 92, 94 are secured in placeby a nut 114. Each of the nuts 114 includes a scoop 116 that directs andgathers lubricant that is exhausted from the lubricant transfer bearingassembly 84. Lubricant indicated by arrows 25 is exhausted from theinterface between the transfer bearing assembly 84 and the secondbearing 85 and is captured by the scoops 116. Lubricant 25 is thentransferred through passages 118 defined within the nut 114 and theinner races 110. The lubricant is passed to the corresponding taperedbearings 120 of each of the shaft support bearings 92, 94. Lubricant 25is then exhausted from the bearing assemblies 92, 94 and recovered.

The example lubricant transfer bearing assembly 84 is disposed betweenthe first and second support bearings 92, 94 and thereby does notrequire additional axial space. The reduction in axial space providesbenefits in assembly and maintenance of the example gas turbine engine.

Referring to FIGS. 3A, 3B, 3C and 3D, the example lubricant transferbearing assembly 84 includes a link 130 that attaches by way of a pin134 to a static engine structure 36 that includes ears 136. The link 130is attached by way of a pin 134 on a first side that includes ears 134.The link 130 is attached to a boss 138 including ears 142 on a secondside by way of a ball 140 and pin 144. The ball 140 allows the lubricanttransfer bearing assembly 84 to flex with the torque frame shaft 80 toaccommodate misalignment and movement during operation. A plurality offeed tubes 106 are in communication with the lubricant transfer assembly84 to supply a desired lubricant flow to different structures of thegeared architecture 48.

Referring to FIG. 3D, the example lubricant transfer bearing assembly 84includes a housing 150 that receives the seal head 108 of the feed tube106. The housing 150 includes passages 145, 146, 152 and 154 thatcommunicate lubricant to the second bearing surface 85 that is definedin this example by the torque shaft 80. The torque shaft 80 includesopenings 110. The example openings 110 are configured as races 156, 158and 160. The races 156, 158 and 160 are annular grooves about the torqueshaft 80 that provide for the communication of lubricant to specificpassages and to specific openings 162, 164 and 166 that allow for thecommunication of lubricant to specific locations and different conduits90.

Referring to FIG. 4, the example conduit 90 is supported between thecarrier 72 and the manifold 98. Each end of the conduit 90 includesseals 168 to prevent leakage. The example conduit 90 includes a spacingthat accommodates relative movement due to thermal expansion and othermisalignments that may occur during operation while still maintaining adesired lubricant flow path from the lubricant manifold 98 to the gearedarchitecture 48.

Referring to FIG. 5, another example fan drive gear system 175 isdisclosed and includes an intermediate passage 172 that is definedwithin the example torque shaft 170. Accordingly, a separate lubricantmanifold is not utilized in this disclosed example. The example torqueshaft 170 is coupled to the hub shaft 78 and defines the intermediatepassage 172. The torque shaft 170 defines a second bearing surface 126and is in communication with the lubricant transfer bearing assembly 84.The hub shaft 78 is coupled to the torque shaft 170 through a splinedconnection 178 and secured in place by nut 176.

Lubricant supplied through the feed tube 106 is fed through openings inthe transfer bearing assembly 84 to the intermediate lubricant passage172. This lubricant indicated by arrows 25 is then communicated to theconduit 90 and thereby to the geared architecture.

As in the previous example, each of the first and second support bearingassemblies 92, 94 includes a nut 114 within a scoop 116 to directlubricant exhausted from the transfer bearing assembly 84. In thisexample, the transfer bearing assembly 84 includes a positive jet 180that positively ejects a lubricant against the scoop 116 throughpassages 118 defined within the inner race 110 of each of the shaftsupport bearing assemblies 92, 94.

Referring to FIGS. 1 and 2, the disclosed fan drive gear system 66enables a simplified non-blind assembly of the fan shaft assembly 76 andlubricant transfer bearing assembly 84. Assembly may be performedaccording to one disclosed example embodiment by attaching the torqueshaft 80 to a component of the geared architecture 48. In this example,the torque shaft 80 is attached to the carrier assembly 72. Once thetorque shaft 80 is attached, the first support bearing assembly 92 isassembled to the static engine structure 36 to support the torque shaft80.

Once the first support bearing assembly 92 is assembled, the lubricanttransfer bearing assembly 84 is assembled onto the outer surface of thetorque shaft 80 to engage the second bearing 85 and interface with theopenings 100 defined through the torque shaft 80 for communicatinglubricant to the lubricant passage 88. The first bearing assembly 92 issecured in place by the nut 114 such that the scoop 116 extends adjacentto one side of the lubricant transfer bearing assembly 84 to capturelubricant expelled during operation. Assembly of the lubricant transferbearing assembly 84 includes assembly of the feed tube 106 through thespacer spring 96. The spacer spring 96 is provided in place and the hubshaft 78 is attached to the torque shaft 80.

Assembly continues by coupling the hub shaft 78 to the torque shaft 80through a splined connection and nut. Once the hub shaft 78 is securedto the torque shaft 80 the second shaft support bearing assembly 94 isassembled to the hub shaft 78 and spaced apart by the spring 96 from thefirst shaft support assembly 92. The feed tube 106 extends through thespacer 96 such that lubricant is feed to both the first and second shaftsupport bearing assemblies 92, 94 and the geared architecture frombetween the shaft support bearing assemblies.

In one example, a lubricant manifold 98 is attached to the torque shaft80 and defines the passage 88 to the geared architecture. The methodincludes attaching the lubricant manifold to the torque shaft 80 andassembling the conduit 90 between the lubricant manifold 98 and thecarrier 72. In another embodiment where the passage 88 is defined withinthe torque shaft 80, the conduit 90 is assembled between the torqueshaft 170 (FIG. 5) and the carrier 72.

Accordingly, disclosed embodiments of a fan drive gear system include atwo piece shaft assembly and lubrication system that eases assembly andsupplies lubricant to both shaft support bearing assemblies and thegeared architecture.

Although an example embodiment has been disclosed, a worker of ordinaryskill in this art would recognize that certain modifications would comewithin the scope of this disclosure. For that reason, the followingclaims should be studied to determine the scope and content of thisdisclosure.

What is claimed is:
 1. A lubrication system comprising: a transferbearing configured to receive a lubricant from a lubricant input; asecond bearing configured to rotate with a fan drive shaft, the transferbearing engages the second bearing between two fan shaft supportbearings and is configured to transfer lubricant from the transferbearing to the second bearing and into at least one lubricant passage;and a conduit fluidly connected to the at least one lubricant passageand configured to deliver lubricant to at least one component of a fandrive gear system.
 2. The lubrication system as recited in claim 1including a first race on the transfer bearing configured to transferlubricant to a first opening in registration with the at least onelubricant passage.
 3. The lubrication system as recited in claim 1,wherein the second bearing comprises a portion of the fan drive shaftand the at least one lubricant passage is defined within the fan driveshaft.
 4. The lubrication system as recited in claim 1, wherein thesecond bearing comprises a portion of the fan drive shaft and alubricant manifold is attached for rotation with the fan drive shaft andincludes the at least one lubricant passage.
 5. The lubrication systemas recited in claim 1, including a feed tube supplying lubricant to thetransfer bearing, wherein the feed tube extends through an opening in aspacer defining a desired spacing between two fan drive shaft supportbearings.
 6. The lubrication system as recited in claim 5, including atleast one fastener securing at least one of the two fan drive shaftsupport bearings in position, wherein the at least one fastener includesa scoop for catching and directing lubricant to one of the two fan driveshaft support bearings.
 7. The lubrication system as recited in claim 5,wherein the two fan drive shaft support bearings comprise taperedbearings.
 8. The lubrication system as recited in claim 5, wherein thetwo fan drive shaft support bearings comprise roller bearings.
 9. Thelubrication system as recited in claim 5, wherein the two fan driveshaft support bearings comprise ball bearings.
 10. The lubricationsystem as recited in claim 1, wherein the transfer bearing and thesecond bearing are disposed about a rotational axis.
 11. The lubricationsystem as recited in claim 1, wherein the conduit is parallel to therotational axis.
 12. A fan drive gear system for a gas turbine enginecomprising: a first fan shaft coupled to a second fan shaft; a firstshaft support bearing assembly disposed about the first fan shaft and asecond shaft support bearing assembly disposed about the second fanshaft; a planetary gear system coupled to the second fan shaft; atransfer bearing configured to receive lubricant from a lubricant inputengaged to the first, fan shaft, the transfer bearing disposedaxially—between the first shaft support bearing assembly and the secondshaft support bearing assembly; a second bearing configured to rotatewith the second fan shaft and receive lubricant from the transferbearing and communicate lubricant to at least one lubricant passage; anda conduit fluidly connecting the at least one lubricant passage to theplanetary gear system.
 13. The system as recited in claim 12, includinga first race on the transfer bearing configured to transfer lubricant tothe at least one lubricant passage.
 14. The system as recited in claim12, including a carrier supporting rotation of a plurality of planetgears and the second shaft comprises a torque shaft attached to thecarrier.
 15. The system as recited in claim 14, wherein the at least onelubricant passage is defined within the torque shaft.
 16. The system asrecited in claim 15, including a first nut holding the first shaftsupport bearing in place and a second nut holding the second shaftsupport bearing in place, wherein each of the first nut and the secondnut includes a scoop for catching and directing lubricant to acorresponding one of the first and second shaft support bearings. 17.The system as recited in claim 12, including a lubricant manifoldattached to the second shaft and defining the at least one lubricantpassage.
 18. The system as recited in claim 12, including a spacerbetween the first shaft support bearing assembly and the second shaftsupport bearing assembly.
 19. The system as recited in claim 18,including a feed tube extending through the spacer to the transferbearing.
 20. A method of assembling a fan drive gear system comprising:attaching a torque shaft to a component of a fan drive gear system;assembling a first shaft support bearing to the torque shaft andsecuring the first shaft support bearing with a first fastener;assembling a transfer bearing to the torque shaft for communicatinglubricant to at least one lubricant passage; coupling a hub shaft to thetorque shaft; assembling a second shaft support bearing to the hub shaftand securing the second shaft support bearing with a second fastenerspaced apart from the first shaft support bearing; and attaching alubricant manifold to the torque shaft including the at least onelubricant passage.
 21. The method of assembling the fan drive gearsystem as recited in claim 20, including assembling a conduit fortransferring lubricant from the at least one lubricant passage to thecomponent of the fan drive gear system.
 22. The method of assembling thefan drive gear system as recited in claim 20, wherein the component ofthe fan drive gear system comprises a carrier supporting rotation of aplurality of planetary gears driven by a sun gear and circumscribed by aring gear.
 23. The method of assembling the fan drive gear system asrecited in claim 20, wherein each of the first fastener and the secondfastener includes a scoop and the assembly of each of the fastenerscomprises aligning the scoop relative to the transfer bearing forenabling capture and transfer of lubricant to a corresponding one of thefirst shaft support bearing and the second shaft support bearing.